[REGULATIONS-2008] AE1251 B.E./B.Tech DEGREE EXAMINATION, MARCH 2011 (Aeronautical Engineering) AERODYNAMICS-I TIME: 3 hours Maximum Marks: 100

PART –A (10x2=20 marks)

Answer ALL questions

1. State the law of conservation of mass.

2. What do you mean by steady flow and unsteady flow?

3. Write down the relation between vorticity and circulation.

4. Write down the continuity equation in Cartesian co-ordinate.

5. What is Kutta condition?

6. What is meant by circulation?

7. What is starting vortex?

8. State Kelvin’s circulation theorem.

9. Define shape factor.

10. Define energy thickness. PART –B (5x16=80 marks)

Answers ALL choosing either (a) or (b) of each questions

All questions carry equal marks

11. Derive the continuity equation for a generalized fluid flow in polar co-ordinates.

(16)

OR

12. Derive the energy equation for an incompressible fluid from the basic principle. (16)

13 (i) Define coefficient of pressure and plot the variation of coefficient of pressure for the circular cylinder kept in a uniform flow for both real and inviscid flows. (8)

(ii) Sketch the flow pattern around a spinning cylinder in a uniform stream for various circulation strength indicating clearly the movement of stagnation points. (8) OR

14. Explain the concept of source flow and derive velocity potential function from vortex strength ( (16)

15. Explain Kutta-Joukowski theorem and prove that L= (16)

OR

16. A long circular cylinder of radius K is placed in a steady horizontal stream of velocity U. The cylinder with an angular velocity Calculate the relation = (16)

17. The camber line of a circular arc aerofoil is given by-

Show that at zero lift angle, = -2h

OR 18. Derive the Prandtl's Lifting Line theory and write the assumptions made. (16) 19. If the velocity profile in boundary layer is assumed to be

= ( ) ─ ( )3; Calculate the thickness of the boundary layer, displacement thickness and momentum thickness the shear stress 1.5 m from the leading edge of a plate. (16)

OR

20. Write down the Navier Stokes equation for a laminar, unsteady, compressible, three dimensional viscous flow. (16)